Results of an experimental study of a subsonic flow past aircraft model having “flying wing” form and belonging to the category of small-unmanned aerial vehicles are reported. Quantitative data about the structure of the flow near the model surface were obtained by hot-wire measurements. It was shown, that with the wing sweep angle 34 °the laminar-turbulent transition scenario is identical to the one on a straight wing. The transition occurs through the development of a package of unstable oscillations in the boundary layer separation.


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    Titel :

    Laminar-turbulent transition on the flying wing model


    Beteiligte:
    Pavlenko, A. M. (Autor:in) / Zanin, B. Yu. (Autor:in) / Katasonov, M. M. (Autor:in) / Fomin, Vasily (Herausgeber:in)

    Kongress:

    INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2016): Proceedings of the 18th International Conference on the Methods of Aerophysical Research ; 2016 ; Perm, Russia


    Erschienen in:

    Erscheinungsdatum :

    13.10.2016


    Format / Umfang :

    7 pages





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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